Truss design for multimotored aircraft



June 17 1924} v 1,498,000 A. v. VERVlLLE TRUSS DESIGN FOR MULTIMOTORED AIRCRAFT Filed April 18, '1922 2 Sheets-Shut 1 af bmz June 17 1924.

A. v. VERVILLE muss nssmu FOR mummowonsv AIRCRAFT Filed April 18, 1922 2 Sheets-Sheet 2 iftml 17 .1924.

STATES PATENT to the upper wingJ I ALFRED v. vnnvrnnn, or narrow, care.

- rauss DESIGN FOR munrmoroann' A a h anaemia C I Application filed April 18, 1922. SeriaI'N'o. 555,308.

To all whom it may concern:

Be it known that I, ALFRED V. VERVILLE, a citizen of the United States, residing at Dayton, in the county of Montgomery and State of Ohio, have invented certain new and useful Improvements in Truss Designs for Multimotored Aircraft, of which the following is a specification.

This invention relates in general to multimotored aircraft of the larger type and more specifically to a trussing system com- 'mon to both the landing gear and supportin surfaces or wings.' v

The object of this invention is to reduce the number of exposed struts and wiring and the parasite head resistanc caused thereby, without correspondingly reducing the strength of the truss. -To this end it is proposed to mount the fuselage of the aircraft intermediate the supporting surfaces thereof in such a manner that the truss for the inner bays will be free from wires, but will consist in N aft, and struts extending diagonally from the upper end-of the inner vertical strut to the point of connection of the .fuselage to the lower wing. The truss between the fuselage of the upper wing will consistin plurality of struts extending diagonally from either side of the fuselage to a central point of convergence to their connection It is also proposed to apply this system overtruss design in the landing gear- 2 L With the foregoing. and vother objects which 1 ceeds the present invention resides in the form com'bmation of parts and in thedetails ofv described anding gear to be used in' case? a single set of landing wheels are employed.

Figure 4 is. a side view of the landing geartoube used in case of wheels is used.-

Figure 5 is a similar'view' of a modified .of'the landing gear shown in Fig- N type of a dual set urea.

struts extending fore and,

shall appear as the description pro-f e wings and landing gear ment there is provided a] Referring more particularly';to the drawlngs, the truss is constructed of two or more verticalN struts 2, the ends of said strutsbeing connected to flying or landing wires 4 and 5. In the inner bay next to the fuselage,the usual flying and landing wires are I resent a replaced by the struts 1, vthus e iminate a strong and rigid construction and complicated system ofbracing wires below the connection of the strut 2 to the lower wing 10 at a point 8. It is understood that the strut 1 will be so constructed and mount- 'ed that it will act equally as wellas a com-' pression or tension member in withstandingany normal strain thrust upon it.

The upper wing 9 is connected to the fuselage 12 By means of a strut having c'om- H ponent parts 6 and 7 connected to the fuselage 12 at 15 and 16' and connected to the upper-wing!) at 17. Numerals 19 and 20 represent the rudder and control" wires therefor respectively.

By this construction there is eliminated in both inner bays, all flying and landing wires andalsothe usual wires for bracing the struts connecting the, upper wing tothe fuselage. It will be readily seen that this will present a strong and more rigid truss construction, more easily asse led with fewest adjustments from time to time, and

furthermore considerably reduce the head resistance caused by the presence and vibra- .tion .of such .wires of aircraft. I

The advantages of an auxiliary set of landi11g wheels placed forwardly of the main landing wheels are well known. As more in the conventional type clearly shown in Figure 2'the two sets of wheels are solplaedd withrelation to each other that both sets 'rest on the ground when the fuselage is parallel to the ground. When the rear end tail skid. the front wheels will obviously bejelevated from the ground.

. Referring .to Figure 4:, 10 represents the lower wing of the aircraft. -An N strut 22,

. having-its three component parts integral with each other is provided with a bracing member 22 also integral therewith. -'Ihe,,strut'landing gear construction is con nected in any suitable manner to the lower and'to the axles 18 and 18', of the 'landmg wheels 13 and 13' respectively. It willv be readily seen that strong rigid land-.

m s are be s? by this; arrange? of. the fuselage rests on the I assembled and which will require" the mini- Y muin amount of adjustment from time to.

time as there are no wires -or the like present;

5 A shown inFigure 1, these N struts 22.

are arranged on either side of each landing gear or set of landingwheels; A lateral cross braein member-21 extends fromone' set of whee s to a lower point 23 of the m fuselage and then to the other set of landing wheels on the opposite side of the fuseage.

Figure 5 merely shows the N struts as applied reversely of that form shown in 5 Figure 4, while Figure 3' illustrates a -V type of landing gearwhich is to be. used in struts between said wing struts and said fuselage body.

i 2 In combination with the upper and lower planes of an airplane, a fuselage body substantially between said upper and lower' planes, an Inverted V-shap ed strut linking saidfuselage'body' Withsaid upper plane,

wing struts on either side of said fuselage body, idiagonalvflying and landing struts between said wing struts and said fuselage body and connected to the upper ends of said wing struts.

3. In combination with the upper and 1 lower planes of an airplane, a fuselage body substantially between said upper and lower planes, an inverted V-shaped strut linking said fuselage body with said upper plane, wing struts on either side of said fuselage body, diagonal'flying and landing,struts between said wing struts and said fuselage body and connected to the upper ends of said wing struts, dual' landing gear attached to the lower side of said lower plane, and 50 diagonal bracing members for said duallanding gear attached to a point substantially agreeing. with the meeting point of, said two diagonal wing struts.

In testimony whereof I afli-x my signa 5. ture. v

ALFRED VQVERVILLE, 

